Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations 25921 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (h) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

25–1529. 

Unsafe Condition 

(d) This AD results from a revision to 

subsection 9–1 of the Airbus A330 and A340 

Maintenance Planning Documents (MPD) for 

Life limits/Monitored parts, and subsection 

9–2 of the Airbus A330 MPD for 

Airworthiness Limitations Items. We are 

issuing this AD to prevent fatigue cracking, 

damage, or corrosion, which could result in 

reduced structural integrity of these 

airplanes. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Airworthiness Limitations Revision 

(f) Within 3 months after the effective date 

of this AD, revise the Airworthiness 

Limitations section (ALS) of the Instructions 

for Continued Airworthiness by 

incorporating into the ALS the documents in 

paragraph (f)(1) and (f)(2) of this AD, as 

applicable. 

(1) Airbus Document AI/SE–M4/95A.0089/ 

97, ‘‘A330 Airworthiness Limitations Items,’’

Issue 12, dated November 1, 2003, as 

specified in Section 9–2 of the Airbus A330 

MPD. 

(2) Section 9–1, ‘‘Life limits/Monitored 

parts,’’ Revision 05, dated April 7, 2005, of 

the Airbus A330 and A340 MPDs. 

(g) Except as provided by paragraph (h) of 

this AD: After the actions in paragraph (f) of 

this AD have been accomplished, no 

alternative inspections or inspection 

intervals may be approved for the structural 

elements specified in the documents listed in 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(i) French airworthiness directives F–

2004–024, dated February 18, 2004; F–2005–

069, dated April 27, 2005; and F–2005–070, 

dated April 27, 2005; also address the subject 

of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Document AI/SE–

M4/95A.0089/97, ‘‘A330 Airworthiness 

Limitations Items,’’ Issue 12, dated November 

1, 2003; Section 9–1, ‘‘Life limits/Monitored 

parts,’’ Revision 05, dated April 7, 2005, of 

the Airbus A330 Maintenance Planning 

Document; and Section 9–1, ‘‘Life limits/ 

Monitored parts,’’ Revision 05, dated April 7, 

2005, of the Airbus A340 Maintenance 

Planning Document; as applicable, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. (The 

document and issue number of Airbus 

Document AI/SE–M4/95A.0089/97 are 

contained only on the Title, Record of 

Revision, Summary of Changes, List of 

Effective Pages, Table of Contents, and 

Section 1 pages; no other page of this 

document contains this information. The 

revision number of Section 9–1 of the Airbus 

A330 Maintenance Planning Document and 

Section 9–1 of the Airbus A340 Maintenance 

Planning Document is contained only in the 

Record of Revisions page; no other page of 

these documents contains this information. 

The issue date on the title page of section 9–

1 of the Airbus A340 Maintenance Planning 

Document should be ‘‘April 7, 2005.’’) The 

Director of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/federal_

register/code_of_federal_regulations/ibr_

locations.html. 

Issued in Renton, Washington, on April 20, 

2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–4051 Filed 5–2–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23870; Directorate 

Identifier 2005–NM–022–AD; Amendment 

39–14575; AD 2006–09–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–200 and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A310–200 and –300 series 

airplanes. This AD requires doing 

repetitive rotating probe inspections for 

any crack of the rear spar internal angle 

and the left and right sides of the tee 

fitting, and doing related investigative/ 

corrective actions if necessary. This AD 

also requires modifying the holes in the 

internal angle and tee fitting by cold 

expansion. This AD results from fullscale fatigue tests, which revealed 

cracks in the lower rear spar internal 

angle, and tee fitting. We are issuing this 

AD to detect and correct fatigue cracks 

of the rear spar internal angle and tee 

fitting, which could lead to the rupture 

of the internal angle, tee fitting, and rear 

spar, and consequent reduced structural 

integrity of the wings. 

DATES: This AD becomes effective June 

7, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 7, 2006. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–2797; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 


sroberts on PROD1PC70 with RULES
25922 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all Airbus Model A310–200 

and –300 series airplanes. That NPRM 

was published in the Federal Register 

on February 13, 2006 (71 FR 7449). That 

NPRM proposed to require doing 

repetitive rotating probe inspections for 

any crack of the rear spar internal angle 

and the left and right sides of the tee 

fitting, and doing related investigative/ 

corrective actions if necessary. That 

NPRM also proposed to require 

modifying the holes in the internal 

angle and tee fitting by cold expansion. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. This AD will 

affect about 56 airplanes of U.S. registry. 

Work hours and parts costs vary 

according to the configuration of the 

airplane. 

ESTIMATED COSTS

Action Work hour 

Average 

labor rate 

per hour 

Parts Cost per airplane Fleet cost 

Inspection ............... 16–306 $65 $618–$18,489 $1,658–$38,379, per inspection 

cycle.

$92,848–$2,149,224, per inspection cycle. 

Modification ............ 146–381 65 4,350–15,501 $13,840–$40,266 .......................... $775,040–$2,254,896. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2006–09–05 Airbus: Amendment 39–14575. 

Docket No. FAA–2006–23870; 

Directorate Identifier 2005–NM–022–AD. 

Effective Date 

(a) This AD becomes effective June 7, 2006. 

Affected ADs 

(b) Certain requirements of this AD 

terminate certain requirements of AD 98–26–

01, amendment 39–10942. 

Applicability 

(c) This AD applies to all Airbus Model 

A310–203, –204, –221, and –222 airplanes; 

and Model A310–304, –322, –324, and –325 

airplanes; certificated in any category. 

Unsafe Condition 

(d) This AD results from full-scale fatigue 

tests, which revealed cracks in the lower rear 

spar internal angle and tee fitting. We are 

issuing this AD to detect and correct fatigue 

cracks of the rear spar internal angle and tee 

fitting, which could lead to the rupture of the 

internal angle, tee fitting, and rear spar, and 

consequent reduced structural integrity of the 

wings. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Initial and Repetitive Inspections 

(f) At the later of the times specified in 

paragraphs (f)(1) and (f)(2) of this AD, do a 

rotating probe inspection for any crack of the 

rear spar internal angle located in the center 

wing box and do all applicable related 

investigative and corrective actions in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

57–2047, Revision 06, dated July 13, 2004, 

except as required by paragraphs (k), (l), and 

(m) of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 


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Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations 25923 

(1) Within 1,000 flight cycles or 1,600 

flight hours after the effective date of this AD, 

whichever is first. 

(2) At the applicable time specified in 

Table 1 of this AD. 

TABLE 1.—INITIAL COMPLIANCE TIMES FOR THE REAR SPAR INTERNAL ANGLE

Airplane model and configuration Threshold 

Model A310–203, –204, –221, and –222 airplanes that are not modified 

by Airbus Modifications 06672S6812 and 07387S7974.

Before the accumulation of 10,300 total flight cycles or 16,600 total 

flight hours, whichever is first. 

Model A310–203, –204, –221, and –222 airplanes that are modified by 

Airbus Modifications 06672S6812 and 07387S7974 (modified either 

in production or in accordance with Airbus Service Bulletin A310–57–

2035).

Before the accumulation of 23,400 total flight cycles or 37,700 total 

flight hours, whichever is first. 

Model A310–304, –322, –324, and –325 airplanes that are not modified 

by Airbus Modifications 06672S6812 and 07387S7974.

Before the accumulation of 9,500 total flight cycles or 15,000 total flight 

hours, whichever is first. 

Model A310–304, –322, –324, and –325 airplanes that are modified by 

Airbus Modifications 06672S6812 and 07387S7974 (modified either 

in production or according to Airbus Service Bulletin A310–57–2035).

Before the accumulation of 21,500 total flight cycles or 34,000 total 

flight hours, whichever is first. 

(g) Repeat the inspection specified in 

paragraph (f) of this AD thereafter at the 

applicable time specified in paragraph (g)(1) 

or (g)(2) of this AD. 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Repeat thereafter at intervals 

not to exceed 9,100 flight cycles or 14,650 

flight hours, whichever is first. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes: Repeat thereafter at intervals 

not to exceed 9,500 flight cycles or 15,000 

flight hours, whichever is first. 

(h) At the applicable time specified in 

Table 2 of this AD or within 6 months after 

the effective date of this AD, whichever 

occurs later: Do a rotating probe inspection 

for any crack of the left and right sides of the 

tee fitting, and do all applicable related 

investigative and corrective actions in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

57–2047, Revision 06, dated July 13, 2004, 

except as required by paragraphs (k), (l), and 

(m) of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 

TABLE 2.—INITIAL COMPLIANCE TIMES FOR THE TEE FITTING

Airplane model and configuration Threshold 

Model A310–203, –204, –221, and –222 airplanes that are not modified 

by Airbus Modification 06673S6813.

Before the accumulation of 21,600 total flight cycles or 34,800 total 

flight hours, whichever is first. 

Model A310–203, –204, –221, and –222 airplanes that are modified by 

Airbus Modification 06673S6813 (modified either in production or in 

accordance with Airbus Service Bulletin A310–57–2035).

Before the accumulation of 41,300 total flight cycles or 66,500 total 

flight hours, whichever is first. 

Model A310–304, –322, –324, and –325 airplanes that are not modified 

by Airbus Modification 06673S6813.

Before the accumulation of 17,100 total flight cycles or 27,000 total 

flight hours, whichever is first. 

Model A310–304, –322, –324, and –325 airplanes that are modified by 

Airbus Modification 06673S6813 (modified either in production or in 

accordance with Airbus Service Bulletin A310–57–2035).

Before the accumulation of 32,300 total flight cycles or 51,000 total 

flight hours, whichever is first. 

(i) Repeat the inspection specified in 

paragraph (h) of this AD thereafter at the 

applicable time specified in paragraph (i)(1) 

or (i)(2) of this AD. 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Repeat thereafter at intervals 

not to exceed 10,800 flight cycles or 17,400 

flight hours, whichever is first. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes: Repeat thereafter at intervals 

not to exceed 8,800 flight cycles or 13,900 

flight hours, whichever is first. 

Modification 

(j) For all airplanes except those that are 

modified by Airbus Modifications 

06672S6812, 06673S6813, and 07387S7974 

in production: Within 60 months after the 

effective date of this AD, modify the holes in 

the internal angle and tee fitting and do all 

applicable related investigative and 

corrective actions by accomplishing all the 

actions specified in the Accomplishment 

Instructions of Airbus Service Bulletin A310–

57–2035, Revision 08, dated September 19, 

2005, except as required by paragraph (k) of 

this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 

Contact the FAA 

(k) Where Airbus Service Bulletin A310–

57–2035, Revision 08, dated September 19, 

2005; and Airbus Service Bulletin A310–57–

2047, Revision 06, dated July 13, 2004; 

specify to contact the manufacturer if certain 

cracks are found, before further flight, repair 

those conditions according to a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) (or its 

delegated agent). 

Touch-and-Go Flights 

(l) All touch-and-go landings must be 

counted in determining the total number of 

flight cycles between consecutive 

inspections. 

No Reporting Required 

(m) Although Airbus Service Bulletin 

A310–57–2047, Revision 06, dated July 13, 

2004, specifies to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

Actions Accomplished According to 

Previous Issues of Service Bulletins 

(n) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–57–2047, 

Revision 03, dated November 26, 1997; 

Revision 04, dated March 5, 1999; or 

Revision 05, dated August 3, 2000; are 

considered acceptable for compliance with 

the corresponding actions specified in 

paragraphs (f) through (i) of this AD. 

(o) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–57–2035, 

Revision 1, dated October 13, 1989; Revision 

2, dated February 26, 1990; Revision 3, dated 

May 23, 1990; Revision 4, dated April 15, 

1991; Revision 5, dated May 27, 1992; 

Revision 6, dated March 8, 1994; or Revision 

7, dated April 17, 1996; are considered 

acceptable for compliance with the 

corresponding actions specified in paragraph 

(j) of this AD. 


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25924 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations 

Related AD 

(p) Accomplishing the initial inspections 

specified in paragraphs (f) and (g) of this AD 

terminates the requirements specified in 

paragraph (o) of AD 98–26–01. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(r) French airworthiness directive F–2005–

001, dated January 5, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(s) You must use Airbus Service Bulletin 

A310–57–2047, Revision 06, dated July 13, 

2004; and Airbus Service Bulletin A310–57–

2035, Revision 08, dated September 19, 2005; 

as applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. Airbus Service Bulletin A310–57–

2047, Revision 06, dated July 13, 2004, 

includes the following effective pages: 

Page Nos. Revision level 

shown on page Date shown on page 

1–8, 10–15, 17, 18, 22–25, 33, 37 ........................................................................................................... 06 ..................... July 13, 2004. 

9, 16, 21, 30, 45, 46, 75–80, 95, 96 ........................................................................................................ 05 ..................... August 3, 2000. 

19, 20, 27–29, 35, 36, 47–56, 61–74 ....................................................................................................... Original ............. February 26, 1991. 

26, 31, 32, 34, 39–44, 59, 60, 81–94 ....................................................................................................... 04 ..................... March 5, 1999. 

38 .............................................................................................................................................................. 1 ....................... January 4, 1996. 

57, 58 ........................................................................................................................................................ 2 ....................... January 22, 1997. 

The Director of the Federal Register 

approved the incorporation by reference of 

these documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 20, 

2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–4052 Filed 5–2–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23886; Directorate 

Identifier 2005–NM–255–AD; Amendment 

39–14574; AD 2006–09–04] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 900EX Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Dassault Model Falcon 900EX airplanes. 

This AD requires inspecting the number 

2 engine left- and right-hand forward 

mounts for missing rivets, and installing 

rivets if necessary. This AD results from 

reports of two missing rivets in the front 

section of the central engine mast 

discovered on airplanes in service and 

in production. We are issuing this AD 

to detect and correct missing rivets in 

the front section of the central engine 

mast, which could result in reduced 

structural integrity of the central engine 

mast, possible separation of the engine 

from the airplane during flight, and 

consequent loss of control of the 

airplane. 

DATES: This AD becomes effective June 

7, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 7, 2006. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 

07606, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, WA 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Dassault Model Falcon 

900EX airplanes. That NPRM was 

published in the Federal Register on 

February 15, 2006 (71 FR 7874). That 

NPRM proposed to require inspecting 

the number 2 engine left- and right-hand 

forward mounts for missing rivets, and 

installing rivets if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 


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